EP3539878A1 - Turbine engine comprising a nacelle provided with a fan cowl and a stationary structure - Google Patents

Turbine engine comprising a nacelle provided with a fan cowl and a stationary structure Download PDF

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Publication number
EP3539878A1
EP3539878A1 EP19156324.6A EP19156324A EP3539878A1 EP 3539878 A1 EP3539878 A1 EP 3539878A1 EP 19156324 A EP19156324 A EP 19156324A EP 3539878 A1 EP3539878 A1 EP 3539878A1
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EP
European Patent Office
Prior art keywords
outer shell
turbojet engine
fixed
engine
flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19156324.6A
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German (de)
French (fr)
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EP3539878B1 (en
Inventor
Frédéric RIDRAY
Frédéric PIARD
Pascal Gardes
José GONCALVES
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Airbus Operations SAS
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Airbus Operations SAS
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Publication of EP3539878A1 publication Critical patent/EP3539878A1/en
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Publication of EP3539878B1 publication Critical patent/EP3539878B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/04—Power-plant nacelles, fairings, or cowlings associated with fuselages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
    • F02K1/625—Reversing jet main flow by blocking the rearward discharge by means of flaps the aft end of the engine cowling being movable to uncover openings for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a turbojet engine comprising a nacelle equipped with a fan casing and a fixed structure supporting a movable assembly that moves in translation relative to the fixed structure, and an aircraft comprising at least one such turbojet double flow.
  • An aircraft has a fuselage on each side of which is attached a wing. Under each wing is suspended at least one turbojet turbojet. Each turbojet engine is fixed under the wing by means of a mast which is fixed between the wing structure and the structure of the turbojet engine.
  • a turbojet engine described for example in the patent application WO2014 / 007875 , comprises a motor and a nacelle which is fixed around the engine and which delimits between them a secondary vein.
  • the nacelle comprises a fan casing which is arranged around the blower and the engine.
  • the nacelle also has a movable assembly that moves from front to rear to release a window between the secondary vein and the outside.
  • the movable assembly also carries inner shutters where each is movable to take an extended position in which it is positioned across the secondary vein to deflect the secondary flow outward through the window.
  • the moving assembly moves on a fixed structure which is itself fixed around the fan casing.
  • the mobile assembly also carries a ramp, fixed to the fixed structure, which directs the secondary flow.
  • This ramp is also called “Fan ramp” in English terminology.
  • An object of the present invention is to provide a turbofan engine which comprises a nacelle equipped with a fan casing and a fixed structure on which a moving assembly moves and where the fixation of the fixed structure is optimized.
  • Such a turbojet allows a simplification of the assembly and allows among other things to fix the ramp directly to the outer shell.
  • the Fig. 1 shows an aircraft 10 which comprises a fuselage 12 on each side of which is fixed a wing 14 which carries at least one turbojet engine 100 according to the invention.
  • the attachment of the turbojet engine 100 under wing 14 is effected via a mast 16.
  • the turbojet engine 100 has a nacelle 102.
  • the Fig. 2 and the Fig. 3 show the turbojet engine 100 which also has a motor 20 which is housed inside the nacelle 102.
  • the nacelle 102 comprises a fan casing 206 arranged around the motor 20.
  • the motor 20 is materialized on the Fig. 2 by its front cone and its fan 22 housed inside the fan casing 206 at the air inlet of the nacelle 102.
  • X is called the longitudinal axis of the turbojet engine 100 which is parallel to the longitudinal axis of the aircraft 10 and is oriented positively towards the front of the aircraft 10.
  • Y the transverse axis which is horizontal when the aircraft is on the ground, and Z the vertical axis when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.
  • a secondary vein in which circulates a secondary flow 50 is delimited between the motor 20 and the nacelle 102, and more particularly between the fan casing 206 and the motor 20.
  • a mass of air is sucked in by the air inlet and then expelled at the rear by the fan 22.
  • the air mass is divided, from upstream to downstream in a direction d a flow of air passing through the turbojet engine 100 and substantially parallel to the longitudinal axis X, in a primary flow, which circulates in a primary air flow, and in a secondary flow 50, which is concentric with the flow primary and circulates in the secondary vein, or blower duct.
  • the two veins are separated by an interveine.
  • the primary flow crosses from upstream to downstream relative to the air flow, the various elements of the engine, namely a compressor stage, comprising for example a low pressure compressor and a high pressure compressor downstream of the low pressure compressor, a combustion chamber, a turbine stage, comprising for example a high pressure turbine and a low pressure turbine downstream of the high pressure turbine.
  • a compressor stage comprising for example a low pressure compressor and a high pressure compressor downstream of the low pressure compressor
  • a combustion chamber a combustion chamber
  • a turbine stage comprising for example a high pressure turbine and a low pressure turbine downstream of the high pressure turbine.
  • Structural casings are mounted around the elements of the turbojet engine 100 and allow to stiffen it in order to limit its distortions in operation.
  • the fan 22 is streamlined by the fan casing 206 ("fan casing" in English terminology) and the motor elements 20 are surrounded, from upstream to downstream, by a low pressure compressor casing which surrounds the compressor low pressure, a high pressure compressor housing that surrounds the high compressor pressure, then a crankcase, said "core-turbine” casing in aviation language that surrounds the combustion chamber and the high pressure and low pressure turbines.
  • the turbojet engine 100 further comprises an intermediate casing 302 having a hub portion 304 and an outer shell 306 which is cylindrical and radially spaced from the hub 304 by the secondary duct and attached to the hub 304 via arms 308 ("outlet guide”). vanes “or” OGV “in English terminology) which enable the secondary flux 50 to be straightened.
  • the outer shell 306 is also called "OGV ring" in English terminology.
  • the outer shell 306 is located behind and in continuity with the fan casing 206 and extends the latter to delimit externally the secondary vein while the outer portion of the hub 304 internally delimits the secondary vein.
  • the turbojet engine 100 has a fixed structure 208 which is fixed to the outer shell 306 and which carries a movable assembly 210 (visible only on the Fig. 2 ).
  • the moving assembly 210 which here takes the form of a perforated half-cylinder port and a perforated half-cylinder starboard (not seen on the Fig. 2 ), is mounted movable in translation in a translation direction parallel to the longitudinal axis X between an advanced position and a retracted position. In the retracted position, the moving assembly 210 is moved towards the rear of the nacelle 102 so as to release a window 211 between the secondary vein and the outside of the nacelle 102. In the advanced position, the window 211 is closed by the elements constituting the moving assembly 210.
  • the moving assembly 210 carries interior flaps 212 where each is movable between a retracted position in which the inner flap 212 is outside the secondary vein and an extended position in which the inner flap 212 is positioned across the secondary vein for deflect the secondary flow 50 outward through the window 211. In the deployed position, the inner flaps 212 are oriented towards the motor 20.
  • the inner flaps 212 are in the retracted position when the moving assembly 210 is in the advanced position, and the inner flaps 212 can take the extended position only when the moving assembly 210 is in the retracted position.
  • outer flaps may also be mounted on the movable assembly 210. These outer flaps function as the inner flaps 212 by unfolding outwardly.
  • Each inner or outer flap is articulated by its rear edge to the movable assembly 210 on hinges 213 while the opposite free edge is positioned forwardly in the retracted position and towards the engine 20 in the deployed position for the inner flaps 212 and outward in the extended position for the outer shutters.
  • Stunts can also be set up across window 211.
  • the mobile assembly 210 is not described in detail because it is known to those skilled in the art and can take different forms.
  • the movable assembly 210 is displaced by any appropriate means, for example cylinders or ball screws.
  • the movements of the inner and outer flaps are provided by any appropriate means, such as cylinders or ball screws.
  • the fixed structure 208 is fixed to the outer shell 306 by a 12 hour beam 250, a beam 6 hours 252, a beam 3 hours 254 and a beam 9 hours not visible but identical to the beam 3 hours 254.
  • Each beam extends parallel to the longitudinal axis X.
  • the turbojet engine 100 also comprises a ramp 402 ("Fan ramp") which directs the secondary flow 50 at the outlet of the outer shell 306 and the ramp 402 is fixed to the outer shell 306.
  • the ramp 402 generally takes the form of a widening cone at the outlet of the outer shell 306.
  • the attachment of the ramp 402 and the fixed structure 208 to the outer shell 306 allows space saving by reducing the number of components and therefore a reduction in the thickness of the nacelle 102, which improves the aerodynamics.
  • the ramp 402 has a skirt 404 which is disposed around the outer shell 306 to be attached thereto by means of hardware elements 268 such as bolts.
  • Each beam 250, 252, 254 has a first end which is fixed to the fixed structure 208, here the end facing forward, and a second end which is fixed to the outer shell 306, here the end oriented towards the rear.
  • each beam 250, 252, 254 is fixed to the outer shell 306, via a fitting 260, 262, 264 fixed, on the one hand, to the second end, and on the other hand at the outer shell 306.
  • the skirt 404 is disposed between the outer shell 306 and each bracket 260, 262, 264 to be sandwiched between them and thus be maintained.
  • clamp bolts 268 are provided to clamp the bracket 260, 262, 264 and the outer shell 306 by tightening the skirt 404 therebetween.
  • the clamping bolts 268 are shown on the Figs. 5 and 6 and are only schematized by their axes on the Fig. 7 .
  • the axes of the clamping bolts 268 are radial relative to the outer shell 306.
  • fixing the beam 3 hours 254 and the beam 9 hours with the fitting 264 is provided by fasteners 270 such as bolts and whose axes are radial relative to the outer shell 306.
  • fixing the beam 12 hours 250 with the fitting 260 is provided by a pivot connection 281 whose axis is parallel to the longitudinal axis X and which is here made by two yokes 282 secured to the beam 12 hours 250, each receiving a pierced plate 284 integral with the fitting 260.
  • fixing the beam 6 hours 252 with the fitting 262 is provided by fasteners 272 such as bolts and whose axes are parallel to the transverse axis Y.
  • Figs. 8 and 9 show the beams 12 hours 250 and 6 hours 252 in position relative to the fixed structure 208 and without the fittings 260, 262.
  • Each beam 250, 252, 254 is equipped with a stop 280, 283, 285 forming a plane perpendicular to the longitudinal axis X and each fitting 260, 262, 264 has an abutment 290, 292, 294 which also forms a perpendicular plane to the longitudinal axis X and which bears against the stop 280, 283, 285 of the associated beam 250, 252, 254, so as to block the rotation about the vertical axis Z, as well as a stop according to the longitudinal axis X for a recovery of the axial forces.
  • Screws 502 secure the abutments 290, 292 and 294 against the stops 280, 283 and 285.
  • the invention has been more particularly described in the case of a nacelle under a wing but it can be applied to a nacelle located at the rear of the fuselage.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un turboréacteur (100) comportant un moteur (20), une nacelle comportant un carter de soufflante (206), un carter intermédiaire (302) ayant une partie formant un moyeu (304) et une virole extérieure (306) radialement espacée du moyeu (304) par une veine secondaire et fixée au moyeu (304) via des bras (308), où la virole extérieure (306) est située en arrière et en continuité du carter de soufflante (206), une structure fixe (208) fixée à la virole extérieure (306), un ensemble mobile monté mobile en translation sur la structure fixe (208), et une rampe fixée à la virole extérieure (306) et destinée à orienter le flux secondaire (50) en sortie de la virole extérieure (306).Un tel turboréacteur permet une simplification de l'assemblage et permet entre autres de fixer la rampe directement à la virole extérieure.The invention relates to a turbojet (100) comprising a motor (20), a nacelle comprising a fan casing (206), an intermediate casing (302) having a portion forming a hub (304) and an outer shell (306) radially. spaced from the hub (304) by a secondary vein and fixed to the hub (304) via arms (308), where the outer shell (306) is located behind and in continuity with the fan casing (206), a fixed structure ( 208) fixed to the outer shell (306), a movable assembly movable in translation on the fixed structure (208), and a ramp fixed to the outer shell (306) and intended to guide the secondary flow (50) at the outlet of the outer shell (306) .This turbojet allows a simplification of the assembly and allows among other things to fix the ramp directly to the outer shell.

Description

La présente invention concerne un turboréacteur double flux qui comporte une nacelle équipée d'un carter de soufflante et d'une structure fixe supportant un ensemble mobile qui se déplace en translation par rapport à la structure fixe, ainsi qu'un aéronef comportant au moins un tel turboréacteur double flux.The present invention relates to a turbojet engine comprising a nacelle equipped with a fan casing and a fixed structure supporting a movable assembly that moves in translation relative to the fixed structure, and an aircraft comprising at least one such turbojet double flow.

Un aéronef comporte un fuselage de chaque côté duquel est fixée une aile. Sous chaque aile est suspendu au moins un turboréacteur double flux. Chaque turboréacteur double flux est fixé sous l'aile par l'intermédiaire d'un mât qui est fixé entre la structure de l'aile et la structure du turboréacteur double flux.An aircraft has a fuselage on each side of which is attached a wing. Under each wing is suspended at least one turbojet turbojet. Each turbojet engine is fixed under the wing by means of a mast which is fixed between the wing structure and the structure of the turbojet engine.

Un turboréacteur double flux, décrit par exemple dans la demande de brevet WO2014/007875 , comporte un moteur et une nacelle qui est fixée autour du moteur et qui délimite entre eux une veine secondaire.A turbojet engine, described for example in the patent application WO2014 / 007875 , comprises a motor and a nacelle which is fixed around the engine and which delimits between them a secondary vein.

La nacelle comporte un carter de soufflante qui est agencé autour de la soufflante et du moteur. La nacelle comporte également un ensemble mobile qui se déplace de l'avant vers l'arrière pour libérer une fenêtre entre la veine secondaire et l'extérieur.The nacelle comprises a fan casing which is arranged around the blower and the engine. The nacelle also has a movable assembly that moves from front to rear to release a window between the secondary vein and the outside.

L'ensemble mobile porte également des volets intérieurs où chacun est mobile pour prendre une position déployée dans laquelle il se positionne en travers de la veine secondaire pour dévier le flux secondaire vers l'extérieur à travers la fenêtre.The movable assembly also carries inner shutters where each is movable to take an extended position in which it is positioned across the secondary vein to deflect the secondary flow outward through the window.

L'ensemble mobile se déplace sur une structure fixe qui est elle-même fixée autour du carter de soufflante.The moving assembly moves on a fixed structure which is itself fixed around the fan casing.

L'ensemble mobile porte également une rampe, fixée à la structure fixe, qui permet de diriger le flux secondaire. Cette rampe est également appelée « Fan ramp » en terminologie anglo-saxonne.The mobile assembly also carries a ramp, fixed to the fixed structure, which directs the secondary flow. This ramp is also called "Fan ramp" in English terminology.

Pour des raisons de simplification structurelles, il est nécessaire de trouver des solutions optimales pour fixer la structure fixe et la rampe.For reasons of structural simplification, it is necessary to find optimal solutions for fixing the fixed structure and the ramp.

Un objet de la présente invention est de proposer un turboréacteur double flux qui comporte une nacelle équipée d'un carter de soufflante et d'une structure fixe sur laquelle se déplace un ensemble mobile et où la fixation de la structure fixe est optimisée.An object of the present invention is to provide a turbofan engine which comprises a nacelle equipped with a fan casing and a fixed structure on which a moving assembly moves and where the fixation of the fixed structure is optimized.

A cet effet, est proposé un turboréacteur double flux tel que revendiqué dans la revendication 1.For this purpose, a double flow turbojet engine as claimed in claim 1 is proposed.

Un tel turboréacteur permet une simplification de l'assemblage et permet entre autres de fixer la rampe directement à la virole extérieure.Such a turbojet allows a simplification of the assembly and allows among other things to fix the ramp directly to the outer shell.

Les caractéristiques de l'invention mentionnées ci-dessus, ainsi que d'autres, apparaîtront plus clairement à la lecture de la description suivante d'un exemple de réalisation, ladite description étant faite en relation avec les dessins joints, parmi lesquels :

  • la Fig. 1 est une vue de côté d'un aéronef comportant un turboréacteur double flux selon l'invention,
  • la Fig. 2 est une vue de devant et en perspective du turboréacteur double flux selon l'invention,
  • la Fig. 3 est une vue de derrière et en perspective du turboréacteur double flux de la Fig. 2,
  • la Fig. 4 est une vue en coupe du turboréacteur double flux selon la ligne IV-IV de la Fig. 3,
  • la Fig. 5 est une vue en perspective de la fixation au niveau de la poutre 3 heures,
  • la Fig. 6 est une vue en perspective de la fixation au niveau de la poutre 12 heures,
  • la Fig. 7 est une vue en perspective de la fixation au niveau de la poutre 6 heures,
  • la Fig. 8 est une vue en perspective d'un exemple d'une poutre 12 heures, et
  • la Fig. 9 montre une vue en perspective d'un exemple d'une poutre 6 heures.
The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being given in relation to the attached drawings, among which:
  • the Fig. 1 is a side view of an aircraft comprising a turbojet engine according to the invention,
  • the Fig. 2 is a front view and in perspective of the turbojet engine according to the invention,
  • the Fig. 3 is a view from behind and in perspective of the turbojet turbojet of the Fig. 2 ,
  • the Fig. 4 is a sectional view of the turbojet engine according to line IV-IV of the Fig. 3 ,
  • the Fig. 5 is a perspective view of the fixation at the beam 3 hours,
  • the Fig. 6 is a perspective view of the fastening at the level of the beam 12 hours,
  • the Fig. 7 is a perspective view of the attachment at the beam 6 hours,
  • the Fig. 8 is a perspective view of an example of a 12 hour beam, and
  • the Fig. 9 shows a perspective view of an example of a 6-hour beam.

Dans la description qui suit, les termes relatifs à une position sont pris en référence au sens d'avancement de l'aéronef qui se déplace en avant.In the following description, the terms relating to a position are taken with reference to the direction of advance of the aircraft moving forward.

La Fig. 1 montre un aéronef 10 qui comporte un fuselage 12 de chaque côté duquel est fixée une aile 14 qui porte au moins un turboréacteur double flux 100 selon l'invention. La fixation du turboréacteur double flux 100 sous l'aile 14 s'effectue par l'intermédiaire d'un mât 16.The Fig. 1 shows an aircraft 10 which comprises a fuselage 12 on each side of which is fixed a wing 14 which carries at least one turbojet engine 100 according to the invention. The attachment of the turbojet engine 100 under wing 14 is effected via a mast 16.

Le turboréacteur double flux 100 présente une nacelle 102.The turbojet engine 100 has a nacelle 102.

La Fig. 2 et la Fig. 3 montrent le turboréacteur double flux 100 qui présente également un moteur 20 qui est logé à l'intérieur de la nacelle 102.The Fig. 2 and the Fig. 3 show the turbojet engine 100 which also has a motor 20 which is housed inside the nacelle 102.

La nacelle 102 comporte un carter de soufflante 206 agencé autour du moteur 20. Le moteur 20 est matérialisé sur la Fig. 2 par son cône avant et sa soufflante 22 logée à l'intérieur du carter de soufflante 206 au niveau de l'entrée d'air de la nacelle 102.The nacelle 102 comprises a fan casing 206 arranged around the motor 20. The motor 20 is materialized on the Fig. 2 by its front cone and its fan 22 housed inside the fan casing 206 at the air inlet of the nacelle 102.

Dans la description qui suit, et par convention, on appelle X l'axe longitudinal du turboréacteur double flux 100 qui est parallèle à l'axe longitudinal de l'aéronef 10 et orienté positivement vers l'avant de l'aéronef 10, on appelle Y l'axe transversal qui est horizontal lorsque l'aéronef est au sol, et Z l'axe vertical lorsque l'aéronef est au sol, ces trois directions X, Y et Z étant orthogonales entre elles.In the following description, and by convention, X is called the longitudinal axis of the turbojet engine 100 which is parallel to the longitudinal axis of the aircraft 10 and is oriented positively towards the front of the aircraft 10. Y the transverse axis which is horizontal when the aircraft is on the ground, and Z the vertical axis when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

Une veine secondaire dans laquelle circule un flux secondaire 50 est délimitée entre le moteur 20 et la nacelle 102, et plus particulièrement entre le carter de soufflante 206 et le moteur 20.A secondary vein in which circulates a secondary flow 50 is delimited between the motor 20 and the nacelle 102, and more particularly between the fan casing 206 and the motor 20.

Lorsque le turboréacteur double flux 100 fonctionne, une masse d'air est aspirée par l'entrée d'air puis expulsée à l'arrière par la soufflante 22. La masse d'air est divisée, d'amont en aval selon une direction d'un flux d'air traversant le turboréacteur double flux 100 et sensiblement parallèle à l'axe longitudinal X, en un flux primaire, qui circule dans une veine d'air primaire, et en un flux secondaire 50, qui est concentrique avec le flux primaire et circule dans la veine secondaire, ou conduit de soufflante. Les deux veines sont séparées par une interveine.When the double flow turbojet engine 100 operates, a mass of air is sucked in by the air inlet and then expelled at the rear by the fan 22. The air mass is divided, from upstream to downstream in a direction d a flow of air passing through the turbojet engine 100 and substantially parallel to the longitudinal axis X, in a primary flow, which circulates in a primary air flow, and in a secondary flow 50, which is concentric with the flow primary and circulates in the secondary vein, or blower duct. The two veins are separated by an interveine.

Le flux primaire traverse d'amont en aval par rapport au flux d'air, les différents éléments du moteur, à savoir un étage de compresseurs, comprenant par exemple un compresseur basse pression et un compresseur haute pression en aval du compresseur basse pression, une chambre de combustion, un étage de turbines, comprenant par exemple une turbine haute pression et une turbine basse pression en aval de la turbine haute pression.The primary flow crosses from upstream to downstream relative to the air flow, the various elements of the engine, namely a compressor stage, comprising for example a low pressure compressor and a high pressure compressor downstream of the low pressure compressor, a combustion chamber, a turbine stage, comprising for example a high pressure turbine and a low pressure turbine downstream of the high pressure turbine.

Des carters structuraux sont montés autour des éléments du turboréacteur double flux 100 et permettent de le rigidifier afin notamment de limiter ses distorsions en fonctionnement.Structural casings are mounted around the elements of the turbojet engine 100 and allow to stiffen it in order to limit its distortions in operation.

Ainsi, la soufflante 22 est carénée par le carter de soufflante 206 (« carter fan » en terminologie anglo-saxonne) et les éléments du moteur 20 sont entourés, d'amont en aval, par un carter de compresseur basse pression qui entoure le compresseur basse pression, un carter de compresseur haute pression qui entoure le compresseur haute pression, puis un carter moteur, dit carter « core-turbine » en langage aéronautique qui entoure la chambre de combustion et les turbines haute pression et basse pression.Thus, the fan 22 is streamlined by the fan casing 206 ("fan casing" in English terminology) and the motor elements 20 are surrounded, from upstream to downstream, by a low pressure compressor casing which surrounds the compressor low pressure, a high pressure compressor housing that surrounds the high compressor pressure, then a crankcase, said "core-turbine" casing in aviation language that surrounds the combustion chamber and the high pressure and low pressure turbines.

Le turboréacteur double flux 100 comprend en outre un carter intermédiaire 302 ayant une partie formant un moyeu 304 et une virole extérieure 306 qui est cylindrique et radialement espacée du moyeu 304 par la veine secondaire et fixée au moyeu 304 via des bras 308 (« outlet guide vanes » ou « OGV » en terminologie anglo-saxonne) qui permettent de redresser le flux secondaire 50.The turbojet engine 100 further comprises an intermediate casing 302 having a hub portion 304 and an outer shell 306 which is cylindrical and radially spaced from the hub 304 by the secondary duct and attached to the hub 304 via arms 308 ("outlet guide"). vanes "or" OGV "in English terminology) which enable the secondary flux 50 to be straightened.

La virole extérieure 306 est également appelée « OGV ring » en terminologie anglo-saxonne.The outer shell 306 is also called "OGV ring" in English terminology.

La virole extérieure 306 est située en arrière et en continuité du carter de soufflante 206 et prolonge ce dernier pour délimiter extérieurement la veine secondaire tandis que la partie extérieure du moyeu 304 délimite intérieurement la veine secondaire.The outer shell 306 is located behind and in continuity with the fan casing 206 and extends the latter to delimit externally the secondary vein while the outer portion of the hub 304 internally delimits the secondary vein.

Le turboréacteur double flux 100 présente une structure fixe 208 qui est fixée à la virole extérieure 306 et qui porte un ensemble mobile 210 (visible uniquement sur la Fig. 2).The turbojet engine 100 has a fixed structure 208 which is fixed to the outer shell 306 and which carries a movable assembly 210 (visible only on the Fig. 2 ).

L'ensemble mobile 210 qui prend ici la forme d'un demi-cylindre ajouré à bâbord et d'un demi-cylindre ajouré à tribord (non vu sur la Fig. 2), est monté mobile en translation selon une direction de translation parallèle à l'axe longitudinal X entre une position avancée et une position reculée. En position reculée, l'ensemble mobile 210 est déplacé vers l'arrière de la nacelle 102 de manière à libérer une fenêtre 211 entre la veine secondaire et l'extérieur de la nacelle 102. En position avancée, la fenêtre 211 est obturée par les éléments constituant l'ensemble mobile 210.The moving assembly 210 which here takes the form of a perforated half-cylinder port and a perforated half-cylinder starboard (not seen on the Fig. 2 ), is mounted movable in translation in a translation direction parallel to the longitudinal axis X between an advanced position and a retracted position. In the retracted position, the moving assembly 210 is moved towards the rear of the nacelle 102 so as to release a window 211 between the secondary vein and the outside of the nacelle 102. In the advanced position, the window 211 is closed by the elements constituting the moving assembly 210.

L'ensemble mobile 210 porte des volets intérieurs 212 où chacun est mobile entre une position rentrée dans laquelle le volet intérieur 212 est en dehors de la veine secondaire et une position déployée dans laquelle le volet intérieur 212 se positionne en travers de la veine secondaire pour dévier le flux secondaire 50 vers l'extérieur à travers la fenêtre 211. En position déployée, les volets intérieurs 212 sont orientés vers le moteur 20.The moving assembly 210 carries interior flaps 212 where each is movable between a retracted position in which the inner flap 212 is outside the secondary vein and an extended position in which the inner flap 212 is positioned across the secondary vein for deflect the secondary flow 50 outward through the window 211. In the deployed position, the inner flaps 212 are oriented towards the motor 20.

Les volets intérieurs 212 sont en position rentrée lorsque l'ensemble mobile 210 est en position avancée, et les volets intérieurs 212 ne peuvent prendre la position déployée que lorsque l'ensemble mobile 210 est en position reculée.The inner flaps 212 are in the retracted position when the moving assembly 210 is in the advanced position, and the inner flaps 212 can take the extended position only when the moving assembly 210 is in the retracted position.

Pour aider à diriger le flux secondaire 50 traversant la fenêtre 211 vers l'avant de l'aéronef 10, des volets extérieurs (non représentés ici) peuvent également être montés sur l'ensemble mobile 210. Ces volets extérieurs fonctionnent comme les volets intérieurs 212 en se déployant vers l'extérieur.To help direct the secondary flow 50 passing through the window 211 towards the front of the aircraft 10, outer flaps (not shown here) may also be mounted on the movable assembly 210. These outer flaps function as the inner flaps 212 by unfolding outwardly.

Chaque volet intérieur ou extérieur est articulé par son bord arrière à l'ensemble mobile 210 sur des charnières 213 tandis que le bord libre opposé se positionne vers l'avant en position rentrée et vers le moteur 20 en position déployée pour les volets intérieurs 212 et vers l'extérieur en position déployée pour les volets extérieurs.Each inner or outer flap is articulated by its rear edge to the movable assembly 210 on hinges 213 while the opposite free edge is positioned forwardly in the retracted position and towards the engine 20 in the deployed position for the inner flaps 212 and outward in the extended position for the outer shutters.

Des cascades peuvent également être mises en place en travers de la fenêtre 211.Stunts can also be set up across window 211.

L'ensemble mobile 210 n'est pas décrit plus en détail car il est connu de l'homme du métier et peut prendre différentes formes.The mobile assembly 210 is not described in detail because it is known to those skilled in the art and can take different forms.

Le déplacement de l'ensemble mobile 210 est réalisé par tous moyens appropriés, comme par exemple des vérins ou des vis à billes. De la même manière, les déplacements des volets intérieurs et extérieurs sont assurés par tous moyens appropriés, comme par exemple des vérins ou des vis à billes.The movable assembly 210 is displaced by any appropriate means, for example cylinders or ball screws. In the same way, the movements of the inner and outer flaps are provided by any appropriate means, such as cylinders or ball screws.

La structure fixe 208 est fixée à la virole extérieure 306 par une poutre 12 heures 250, une poutre 6 heures 252, une poutre 3 heures 254 et une poutre 9 heures non visible mais identique à la poutre 3 heures 254. Chaque poutre s'étend parallèlement à l'axe longitudinal X.The fixed structure 208 is fixed to the outer shell 306 by a 12 hour beam 250, a beam 6 hours 252, a beam 3 hours 254 and a beam 9 hours not visible but identical to the beam 3 hours 254. Each beam extends parallel to the longitudinal axis X.

Comme le montre la Fig. 4, le turboréacteur double flux 100 comporte également une rampe 402 (« Fan ramp ») qui oriente le flux secondaire 50 en sortie de la virole extérieure 306 et la rampe 402 est fixée à la virole extérieure 306. La rampe 402 prend globalement la forme d'un cône s'élargissant en sortie de la virole extérieure 306.As shown in Fig. 4 , the turbojet engine 100 also comprises a ramp 402 ("Fan ramp") which directs the secondary flow 50 at the outlet of the outer shell 306 and the ramp 402 is fixed to the outer shell 306. The ramp 402 generally takes the form of a widening cone at the outlet of the outer shell 306.

La fixation de la rampe 402 et de la structure fixe 208 à la virole extérieure 306 permet un gain de place par réduction du nombre de composants et donc une réduction de l'épaisseur de la nacelle 102, ce qui améliore l'aérodynamisme.The attachment of the ramp 402 and the fixed structure 208 to the outer shell 306 allows space saving by reducing the number of components and therefore a reduction in the thickness of the nacelle 102, which improves the aerodynamics.

En outre, dans la mesure où la rampe 402 n'est plus fixée à l'ensemble mobile, il est possible d'accoler la rampe 402 juste à l'arrière de la virole extérieure 306 sans qu'il soit nécessaire de prévoir un jeu de fonctionnement important.In addition, insofar as the ramp 402 is no longer attached to the moving assembly, it is possible to join the ramp 402 just behind the outer shell 306 without the need to provide a set important operation.

La rampe 402 présente une jupe 404 qui est disposée autour de la virole extérieure 306 afin d'y être fixée, ici grâce à des éléments de visserie 268 tels que des boulons.The ramp 402 has a skirt 404 which is disposed around the outer shell 306 to be attached thereto by means of hardware elements 268 such as bolts.

Chaque poutre 250, 252, 254, présente une première extrémité qui est fixée à la structure fixe 208, ici l'extrémité orientée vers l'avant, et une deuxième extrémité qui est fixée à la virole extérieure 306, ici l'extrémité orientée vers l'arrière.Each beam 250, 252, 254 has a first end which is fixed to the fixed structure 208, here the end facing forward, and a second end which is fixed to the outer shell 306, here the end oriented towards the rear.

La deuxième extrémité de chaque poutre 250, 252, 254 est fixée à la virole extérieure 306, par l'intermédiaire d'une ferrure 260, 262, 264 fixée, d'une part, à la deuxième extrémité, et, d'autre part, à la virole extérieure 306.The second end of each beam 250, 252, 254 is fixed to the outer shell 306, via a fitting 260, 262, 264 fixed, on the one hand, to the second end, and on the other hand at the outer shell 306.

La jupe 404 est disposée entre la virole extérieure 306 et chaque ferrure 260, 262, 264 afin d'être prise en sandwich entre elles et être ainsi maintenue.The skirt 404 is disposed between the outer shell 306 and each bracket 260, 262, 264 to be sandwiched between them and thus be maintained.

Afin d'assurer la fixation de chaque ferrure 260, 262, 264 à la virole extérieure 306, des boulons de serrage 268 sont prévus pour serrer la ferrure 260, 262, 264 et la virole extérieure 306 en serrant la jupe 404 entre elles. Les boulons de serrage 268 sont représentés sur les Figs. 5 et 6 et sont uniquement schématisés par leurs axes sur la Fig. 7. Les axes des boulons de serrage 268 sont radiaux par rapport à la virole extérieure 306.In order to secure each bracket 260, 262, 264 to the outer shell 306, clamp bolts 268 are provided to clamp the bracket 260, 262, 264 and the outer shell 306 by tightening the skirt 404 therebetween. The clamping bolts 268 are shown on the Figs. 5 and 6 and are only schematized by their axes on the Fig. 7 . The axes of the clamping bolts 268 are radial relative to the outer shell 306.

Dans le mode de réalisation de l'invention présenté à la Fig. 5, la fixation de la poutre 3 heures 254 et de la poutre 9 heures avec la ferrure 264 est assurée par des éléments de visserie 270 tels que des boulons et dont les axes sont radiaux par rapport à la virole extérieure 306.In the embodiment of the invention presented in Fig. 5 , fixing the beam 3 hours 254 and the beam 9 hours with the fitting 264 is provided by fasteners 270 such as bolts and whose axes are radial relative to the outer shell 306.

Dans le mode de réalisation de l'invention présenté à la Fig. 6, la fixation de la poutre 12 heures 250 avec la ferrure 260 est assurée par une liaison pivot 281 dont l'axe est parallèle à l'axe longitudinal X et qui est réalisée ici par deux chapes 282 solidaires de la poutre 12 heures 250, chacune recevant une plaque percée 284 solidaire de la ferrure 260.In the embodiment of the invention presented in Fig. 6 , fixing the beam 12 hours 250 with the fitting 260 is provided by a pivot connection 281 whose axis is parallel to the longitudinal axis X and which is here made by two yokes 282 secured to the beam 12 hours 250, each receiving a pierced plate 284 integral with the fitting 260.

Dans le mode de réalisation de l'invention présenté à la Fig. 7, la fixation de la poutre 6 heures 252 avec la ferrure 262 est assurée par des éléments de visserie 272 tels que des boulons et dont les axes sont parallèles à l'axe transversal Y.In the embodiment of the invention presented in Fig. 7 , fixing the beam 6 hours 252 with the fitting 262 is provided by fasteners 272 such as bolts and whose axes are parallel to the transverse axis Y.

Les Figs. 8 et 9 montrent les poutres 12 heures 250 et 6 heures 252 en position par rapport à la structure fixe 208 et sans les ferrures 260, 262.The Figs. 8 and 9 show the beams 12 hours 250 and 6 hours 252 in position relative to the fixed structure 208 and without the fittings 260, 262.

Chaque poutre 250, 252, 254 est équipée d'une butée 280, 283, 285 formant un plan perpendiculaire à l'axe longitudinal X et chaque ferrure 260, 262, 264 présente une contrebutée 290, 292, 294 qui forme également un plan perpendiculaire à l'axe longitudinal X et qui est en appui contre la butée 280, 283, 285 de la poutre 250, 252, 254 associée, afin de bloquer la rotation autour de l'axe vertical Z, ainsi qu'un arrêt selon l'axe longitudinal X pour une reprise des efforts axiaux.Each beam 250, 252, 254 is equipped with a stop 280, 283, 285 forming a plane perpendicular to the longitudinal axis X and each fitting 260, 262, 264 has an abutment 290, 292, 294 which also forms a perpendicular plane to the longitudinal axis X and which bears against the stop 280, 283, 285 of the associated beam 250, 252, 254, so as to block the rotation about the vertical axis Z, as well as a stop according to the longitudinal axis X for a recovery of the axial forces.

Des vis 502 assurent la fixation des contrebutées 290, 292 et 294 contre les butées 280, 283 et 285.Screws 502 secure the abutments 290, 292 and 294 against the stops 280, 283 and 285.

L'implantation particulière des éléments de fixation entre les poutres, les ferrures et la virole extérieure 306, ainsi que celle des butées et contrebutées permettent de compenser les efforts transmis depuis le moteur 20.The particular implantation of the fastening elements between the beams, the fittings and the outer shell 306, as well as that of the abutments and abutments compensate for the forces transmitted from the motor 20.

L'invention a été plus particulièrement décrite dans le cas d'une nacelle sous une aile mais elle peut s'appliquer à une nacelle située à l'arrière du fuselage.The invention has been more particularly described in the case of a nacelle under a wing but it can be applied to a nacelle located at the rear of the fuselage.

Claims (10)

Turboréacteur double flux (100) comportant : - un moteur (20), - une structure fixe (208), - une nacelle (102) entourant le moteur (20) et comportant un carter de soufflante (206), où une veine d'un flux secondaire (50) est délimitée entre le carter de soufflante (206) et le moteur (20) et dans laquelle un flux d'air circule, - un ensemble mobile (210) monté mobile en translation sur la structure fixe (208) selon une direction de translation entre une position reculée dans laquelle l'ensemble mobile (210) est déplacé vers l'arrière de manière à libérer une fenêtre (211) entre la veine secondaire et l'extérieur, et une position avancée dans laquelle la fenêtre (211) est obturée par l'ensemble mobile (210), - une rampe (402) destinée à orienter le flux secondaire (50), - un carter intermédiaire (302) ayant une partie formant un moyeu (304), caractérisé en ce que le carter intermédiaire (302) comprend une virole extérieure (306) à laquelle est fixée la structure fixe (208), ladite virole étant radialement espacée du moyeu (304) par la veine secondaire et fixée au moyeu (304) via des bras (308) et est située en arrière et en continuité du carter de soufflante (206), et en ce que la rampe (402) est fixée à la virole extérieure (306) pour orienter le flux secondaire (50) en sortie de la virole extérieure (306).A turbofan engine (100) comprising: a motor (20), a fixed structure (208), a nacelle (102) surrounding the engine (20) and comprising a fan casing (206), where a vein of a secondary flow (50) is delimited between the fan casing (206) and the motor (20) and in which a flow of air circulates, - A movable assembly (210) movably mounted in translation on the fixed structure (208) in a translation direction between a retracted position in which the movable assembly (210) is moved rearwardly so as to release a window (211). ) between the secondary vein and the outside, and an advanced position in which the window (211) is closed by the moving assembly (210), a ramp (402) for orienting the secondary flow (50), an intermediate casing (302) having a portion forming a hub (304), characterized in that the intermediate casing (302) comprises an outer shell (306) to which is fixed the fixed structure (208), said ferrule being radially spaced apart of the hub (304) through the secondary vein and fixed to the hub (304) via arms (308) and is located behind and in continuity with the fan casing (206), and in that the ramp (402) is attached to the outer shell (306) to orient the secondary flow (50) at the outlet of the outer shell (306). Turboréacteur double flux (100) selon la revendication 1, caractérisé en ce que la rampe (402) présente une jupe (404) qui est disposée autour de la virole extérieure (306).A turbofan engine (100) according to claim 1, characterized in that the ramp (402) has a skirt (404) which is disposed around the outer shell (306). Turboréacteur double flux (100) selon l'une des revendications 1 ou 2, caractérisé en ce qu'il comporte une poutre 12 heures (250), une poutre 6 heures (252), une poutre 3 heures (254) et une poutre 9 heures, où chaque poutre présente une première extrémité qui est fixée à la structure fixe (208) et une deuxième extrémité qui est fixée à la virole extérieure (306).A turbofan engine (100) according to one of claims 1 or 2, characterized in that it comprises a beam 12 hours (250), a beam 6 hours (252), a beam 3 hours (254) and a beam 9 hours, where each beam has a first end which is fixed to the fixed structure (208) and a second end which is attached to the outer shell (306). Turboréacteur double flux (100) selon la revendication 3, caractérisé en ce que la deuxième extrémité de chaque poutre (250, 252, 254) est fixée à la virole extérieure (306), par l'intermédiaire d'une ferrure (260, 262, 264) fixée, d'une part, à la deuxième extrémité, et, d'autre part, à la virole extérieure (306).A turbofan engine (100) according to claim 3, characterized in that the second end of each beam (250, 252, 254) is attached to the outer shell (306), by means of a fitting (260, 262, 264) fixed, on the one hand, to the second end, and, on the other hand, to the outer shell (306). Turboréacteur double flux (100) selon la revendication 4, caractérisé en ce que lorsque la rampe (402) présente une jupe (404) qui est disposée autour de la virole extérieure (306), la jupe (404) est prise en sandwich entre la virole extérieure (306) et chaque ferrure (260, 262, 264), et le turboréacteur double flux (100) comporte des boulons de serrage (268) pour serrer la ferrure (260, 262, 264) contre la virole extérieure (306).A turbofan engine (100) according to claim 4, characterized in that when the ramp (402) has a skirt (404) which is arranged around the outer shell (306), the skirt (404) is sandwiched between the outer ferrule (306) and each fitting (260, 262, 264), and the turbojet engine (100) has clamping bolts (268) for clamping the bracket (260, 262, 264) against the outer shroud (306) . Turboréacteur double flux (100) selon l'une des revendications 4 à 5, caractérisé en ce que la fixation de la poutre 3 heures (254) et de la poutre 9 heures avec la ferrure (264) est assurée par des éléments de visserie (270) dont les axes sont radiaux par rapport à la virole extérieure (306).Turbo-flow turbojet engine (100) according to one of Claims 4 to 5, characterized in that the fixation of the 3-hour beam (254) and the 9-hour beam with the fitting (264) is ensured by hardware elements ( 270) whose axes are radial relative to the outer shell (306). Turboréacteur double flux (100) selon l'une des revendications 4 à 6, caractérisé en ce que la fixation de la poutre 12 heures (250) avec la ferrure (260) est assurée par une liaison pivot (281) dont l'axe est parallèle à un axe longitudinal X du turboréacteur double flux (100).Turbo-flow turbojet engine (100) according to one of Claims 4 to 6, characterized in that the fixing of the 12-hour beam (250) with the fitting (260) is ensured by a pivot connection (281) whose axis is parallel to a longitudinal axis X of the turbojet engine (100). Turboréacteur double flux (100) selon l'une des revendications 4 à 7, caractérisé en ce que la fixation de la poutre 6 heures (252) avec la ferrure (262) est assurée par des éléments de visserie (272) dont les axes sont parallèles à un axe transversal Y du turboréacteur double flux (100).Turbo-flow turbojet engine (100) according to one of Claims 4 to 7, characterized in that the fixing of the 6-hour beam (252) with the fitting (262) is ensured by fastener elements (272) whose axes are parallel to a transverse axis Y of the turbojet engine (100). Turboréacteur double flux (100) selon l'une des revendications 4 à 8, caractérisé en ce que chaque poutre (250, 252, 254) est équipée d'une butée (280, 283, 285) formant un plan perpendiculaire à un axe longitudinal X du turboréacteur double flux (100) et en ce que chaque ferrure (260, 262, 264) présente une contrebutée (290, 292, 294) formant un plan perpendiculaire à l'axe longitudinal X en appui contre la butée (280, 283, 285) de la poutre (250, 252, 254) associée.Turbo-flow turbojet engine (100) according to one of claims 4 to 8, characterized in that each beam (250, 252, 254) is equipped with a stop (280, 283, 285) forming a plane perpendicular to a longitudinal axis X of the turbojet engine (100) and in that each bracket (260, 262, 264) has a counter-stop (290, 292, 294) forming a plane perpendicular to the longitudinal axis X bearing against the stop (280, 283). , 285) of the associated beam (250, 252, 254). Aéronef (10) comportant au moins un turboréacteur double flux (100) selon l'une des revendications précédentes.Aircraft (10) comprising at least one turbojet engine (100) according to one of the preceding claims.
EP19156324.6A 2018-03-13 2019-02-11 Turbine engine comprising a nacelle provided with a fan cowl and a stationary structure Active EP3539878B1 (en)

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CN110273783A (en) 2019-09-24
US20190283892A1 (en) 2019-09-19
FR3078951A1 (en) 2019-09-20
EP3539878B1 (en) 2020-07-22
CN110273783B (en) 2022-01-25
FR3078951B1 (en) 2020-02-28
US11161619B2 (en) 2021-11-02

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